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Simulation of Thermal Sensor for Thermal Control of Satellite Using COMSOL Multiphysics

G. Mangalgiri BITS Pilani K K BIRLA GOA CAMPUS
Zuarinagar
Goa, India

The actuator comprises of a temperature sensitive composite deflecting beam, a piezoelectric substrate and a field effect transistor. The temperature rise causes an expansion in the composite beam thereby causing it to deflect. The deflecting beam impinges on the piezoelectric crystal and generating voltage.

Response curves for the deflection versus temperature for temperature ranges considered in the safety limit of the spacecraft will be obtained by modelling the equations relating temperature rise and deflection considering laws of physics. The response for deflection versus voltage and deflection versus the final current output of the FET will be obtained.